WO2019010964A1 - 用于冷却涡轮叶片的凹陷-气膜孔冷却结构及气膜冷却装置 - Google Patents

用于冷却涡轮叶片的凹陷-气膜孔冷却结构及气膜冷却装置 Download PDF

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Publication number
WO2019010964A1
WO2019010964A1 PCT/CN2018/074945 CN2018074945W WO2019010964A1 WO 2019010964 A1 WO2019010964 A1 WO 2019010964A1 CN 2018074945 W CN2018074945 W CN 2018074945W WO 2019010964 A1 WO2019010964 A1 WO 2019010964A1
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Prior art keywords
film
cooling
recess
hole
inlet
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PCT/CN2018/074945
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English (en)
French (fr)
Inventor
饶宇
李彦霖
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Shanghai Jiao Tong University
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Shanghai Jiao Tong University
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence

Definitions

  • the present invention relates to the field of cooling technology for high-temperature components of gas turbines or aeroengines, and more particularly to a recess-membrane hole cooling structure and a film cooling device for cooling turbine blades.
  • Film cooling is important for thermal protection of high temperature components of gas turbines/aviation engines, such as turbine blade cooling and combustion chamber cooling.
  • the film cooling usually obtains cooling air from the internal cooling passage of the turbine blade, and the film hole penetrates the wall surface of the turbine blade, and the film cooling hole connects the cooling channel and the external surface of the turbine blade. Therefore, the airflow in the internal cooling passage flows out through the pores of the gas film to the external surface, and as far as possible spreads out on the external surface, thereby isolating the external hot gas flow from the surface of the turbine blade to provide film cooling for the turbine blade.
  • the turbine blades have internal convection cooling and external film cooling.
  • the cooling airflow flows in the internal passage of the turbine blade to convectively cool the blade wall surface, and on the other hand, the airflow in the internal cooling passage flows out through the gas film hole to the outer surface of the blade to form a film cooling.
  • the effect of film cooling is closely related to the fluid flow from the internal passage of the turbine blade into the cooling hole of the film.
  • the matching between the film hole and the internal cooling channel directly affects the flow rate into the film hole and the flow characteristics in the film hole.
  • the conventional film cooling hole is directly connected to the inner channel wall surface, and when the airflow in the inner channel flows through the film cooling hole, flow separation and vortex are easily generated at the entrance of the film hole, and the pressure difference between the inside and outside of the film hole is affected by The formation of reflux in the pores of the gas film, these factors have a blocking effect on the film pores and have a significant adverse effect on the film cooling performance, which is reflected in the following aspects: (1) due to flow separation and backflow in the pores of the film The effect will reduce the flow of cooling air in the pores of the film, thereby directly reducing the cooling performance of the film; (2) the flow adhesion of the film orifice and the flow vortex in the pore of the film make the flow of the gas in the pore of the film increase.
  • the technical problem to be solved by the present invention is to improve the matching between the film hole and the internal flow path of the cooling blade, thereby improving the flow state in the inlet and the film hole of the film hole, and improving the cooling blade.
  • a first aspect of the present invention provides a recess-membrane hole cooling structure for cooling a blade, comprising a recess provided at an inner wall of the cooling blade and a film hole penetrating the cooling blade,
  • the film aperture has an inlet and the inlet is located at the depression.
  • a part of the inlet penetrates a wall surface where the recess is located, that is, a part of the inlet is located on a wall surface where the recess is located, and another part of the inlet is located on a wall surface of the cooling blade except a recess .
  • all of the inlets extend through the wall surface on which the recess is located, i.e., all of the inlets are located on the wall surface on which the recess is located.
  • all of the single inlets are located on the wall on which the recess is located.
  • the inlets of the plurality of film holes are located on the wall on which the recess is located.
  • the recess is recessed into the inner wall surface, and the shape of the recess is a part of a hemisphere, a part of a spherical shape with a bevel, or a curved surface or a teardrop shape with an edge rounding, etc., but is not limited thereto.
  • the gas film hole further has an outlet located at an outer wall of the cooling blade.
  • the outlet of the air film hole is an oblique hole, a sector hole, a cylindrical hole, a prismatic hole, a pyramidal hole or a conical hole, but is not limited thereto.
  • an angle between a center line of the film hole and a wall surface of the cooling blade is 0 to 90°, preferably 30 to 60°.
  • a second aspect of the invention provides a film cooling device comprising a cooling blade, one or more recesses, and one or more film holes, wherein the recess is disposed on an inner wall of the cooling blade, the gas a film hole penetrating the cooling blade, the film hole having an inlet, wherein all of the inlets of the film hole are located at the recess; or a portion of the inlet of the film hole is located at the recess, and another portion is The inlet of the gas film hole is located in an area other than the recess on the inner wall surface of the cooling blade; or the inlet of the plurality of film holes is located in a recess.
  • the inlet of the air film hole is located at the recess, a part of a single inlet is located on a wall surface where the recess is located, and another part of the single inlet is located on a wall surface of the cooling blade except a recess Outside the area.
  • the inlet of the film aperture is located at the recess, all of the single inlets are located on the wall on which the recess is located.
  • the inlets of the plurality of air film holes are located at one recess, the inlets of the plurality of air film holes are located on the wall surface where the recess is located.
  • the recess is recessed into the inner wall surface, and the shape of the recess is a part of a hemisphere, a part of a spherical shape with a bevel, or a curved surface or a teardrop shape with an edge rounding or the like.
  • the gas film hole further has an outlet located at an outer wall of the cooling blade.
  • the outlet of the film hole is an inclined hole, a fan-shaped hole, a cylindrical hole, a prismatic hole, a pyramidal hole or a conical hole.
  • an angle between a center line of the film hole and a wall surface of the cooling blade is 0 to 90°, preferably 30 to 60°.
  • a film cooling apparatus includes a cooling blade and a plurality of the above-described recess-air film hole cooling structures.
  • the cooling blade of the present invention is a turbine blade.
  • the invention has the advantages that when the fluid in the inner flow passage of the cooling blade flows through the recess, a stable low-speed vortex is formed inside the recess, and a good inlet flow condition is created for the air film hole inside the recess.
  • the flow in the pores of the gas film is smoother, and the turbulent energy of the gas flow in the pores of the gas film is also suppressed.
  • the low-speed stable vortex inside the recess avoids the flow separation, flow adhesion and flow recirculation generated by the internal passage flow in the inlet of the gas film hole in the conventional scheme, thereby overcoming the defects caused by the conventional gas film hole setting, and thus the depression-gas of the present invention
  • the membrane pore cooling structure has more excellent cooling performance.
  • FIG. 1 is a schematic structural view of a film cooling device according to a preferred embodiment of the present invention.
  • Figure 2 is a schematic view showing the structure of a single recessed-air film hole according to a preferred embodiment of the present invention
  • Figure 3 is a schematic view showing the structure of a plurality of recessed-air film holes according to a preferred embodiment of the present invention
  • Figure 4 is another schematic view of a recessed-air film aperture structure in accordance with a preferred embodiment of the present invention, wherein a plurality of air film apertures are located in a recess;
  • Figure 5 is a schematic view showing the flow of airflow in the pores of the gas film of the present invention when the flow in the internal passage of the cooling blade is in the same direction as the external main flow;
  • Figure 6 is a schematic view showing the flow in the existing film pores when the flow in the internal passage of the cooling blade is in the same direction as the external main flow;
  • Figure 7 is a schematic view showing the flow of airflow in the pores of the gas film of the present invention when the flow in the internal passage of the cooling blade is reversed from the external main flow;
  • Fig. 8 is a view showing the flow in the existing film pores when the flow in the inner passage of the cooling blade is reversed from the outer main flow.
  • a preferred embodiment of the present invention provides a film cooling apparatus comprising a cooling blade 1, one or more recesses 2, and one or more film holes 3, wherein the recesses 2 Provided on the inner wall 11 of the cooling blade 1, the film hole penetrates the cooling blade 1, the film hole 3 has an inlet, the entrance of all the film holes 3 is located at the recess 2; or the entrance of a part of the film hole 3 is located at the recess 2, The inlet of the other portion of the film hole 3 is located on the inner wall surface 11 of the cooling blade 1 except for the recess 2; or the plurality of film holes 3 are located at a recess 2.
  • the recess 2 and the gas film hole 3 located at the recess 2 constitute a recess-membrane hole cooling structure.
  • the inlet of the gas film hole 3 when the inlet of the gas film hole 3 is located at the recess 2, a part of the single inlet is located on the wall surface where the recess 2 is located, and the other part of the single inlet is located on the wall surface of the cooling blade 1 except the recess 2 (Fig. Not shown).
  • the inlet of the film hole 3 is located at the recess 2
  • all of the inlets are located on the wall on which the recess 2 is located.
  • 2 and 3 show the case where the entire entrance of the single film hole 3 is located on the wall surface where the recess 2 is located.
  • Figure 4 shows that all of the inlets of the plurality of film holes 3 are located on the wall on which the recess 2 is located.
  • the shape of the recess 2 may be a part of a hemisphere, a part of a spherical shape with a bevel, or a curved surface or a teardrop shape with an edge rounded.
  • the shape of the recess 2 can also be designed as desired in other embodiments.
  • the film aperture 3 also has an outlet which is located at the outer wall 12 of the cooling blade 1.
  • the outlet of the gas film hole 3 may be a slanted hole, a scalloped hole, a cylindrical hole, a prismatic hole, a pyramidal hole or a conical hole. In other embodiments, the shape of the outlet of the air film hole 3 can also be designed as needed.
  • the angle between the center line of the film hole 3 and the wall surface of the cooling blade 1 is 0 to 90, preferably 30 to 60.
  • the cooling blade 1 of the present embodiment is a turbine blade.
  • the film cooling device of the present embodiment includes a cooling blade 1 and a single recess-film hole cooling structure (see FIG. 2) or a plurality of recess-film hole cooling structures (see FIG. 3); or one or more single recesses - Multiple film hole cooling structures (see Figure 4).
  • Arrow 4 in the figure indicates the flow direction of the airflow of the outer wall surface of the cooling blade, and arrow 5 indicates the flow direction of the internal airflow of the cooling blade.
  • An advantage of the present embodiment over the prior art is that when the fluid in the inner flow passage of the cooling blade 1 flows through the recess 2, a stable low-speed vortex is formed inside the recess 2, and a gas film hole 3 is created inside the recess 2 A good inlet flow condition makes the flow in the film hole 3 smoother, and the turbulent energy of the gas flow in the film hole 3 is also suppressed.
  • the low-speed stable eddy current inside the recess 2 avoids the flow separation, the flow adhesion and the flow backflow generated by the internal passage flow in the inlet of the air film hole 3 in the conventional scheme, thereby overcoming the defects caused by the conventional air film hole 3 setting, and thus the embodiment
  • the sag-film hole cooling structure has more excellent cooling performance.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

一种用于冷却涡轮叶片的凹陷-气膜孔冷却结构，包括设置在冷却叶片（1）的内壁的凹陷（2）和贯穿冷却叶片（1）的气膜孔（3），气膜孔（3）具有入口，入口位于凹陷（2）处。还公开了一种气膜冷却装置，包括冷却叶片（1）、一个或多个凹陷（2），以及一个或多个气膜孔（3），其中凹陷（2）设置在冷却叶片（1）的内壁上，气膜孔（3）贯穿冷却叶片（1），气膜孔（3）具有入口，全部的气膜孔（3）的入口位于凹陷（2）处；或者一部分气膜孔（3）的入口位于凹陷（2）处，另一部分气膜孔（3）的入口位于冷却叶片（1）的内壁面上除凹陷（2）以外的区域；或者多个气膜孔（3）的入口位于一个凹陷（2）处。该结构的凹陷-气膜冷却结构能够改善气膜孔与冷却叶片内部流道之间的匹配，从而改善气膜孔入口和气膜孔内的流动状态、提高冷却叶片外部壁面的气膜冷却性能。

Description

用于冷却涡轮叶片的凹陷-气膜孔冷却结构及气膜冷却装置
技术领域
本发明涉及燃气轮机或航空发动机高温部件的冷却技术领域，尤其涉及一种用于冷却涡轮叶片的凹陷-气膜孔冷却结构及气膜冷却装置。
背景技术
气膜冷却对于燃气轮机/航空发动机高温部件热防护具有重要意义，如涡轮叶片冷却，燃烧室冷却。气膜冷却通常从涡轮叶片内部冷却通道获取冷却空气，气膜孔贯穿涡轮叶片壁面，气膜冷却孔连接涡轮叶片内部冷却通道与外部表面。因此，内部冷却通道内的气流通过气膜孔流出至外部表面，并尽可能在外部表面延展开来，从而将外部热气流与涡轮叶片表面隔离开，为涡轮叶片提供气膜冷却
涡轮叶片具有内部对流冷却和外部气膜冷却。冷却气流在涡轮叶片内部通道内流动以对流方式冷却叶片壁面，另一方面内部冷却通道内的气流通过气膜孔流出至叶片外部表面形成气膜冷却。
气膜冷却的效果与从涡轮叶片内部通道进入气膜冷却孔内的流体流动状况密切相关。气膜孔与内部冷却通道之间的匹配直接影响到流入气膜孔的流量大小，以及气膜孔内的流动特征。常规的气膜冷却孔与内部通道壁面直接贯通连接，内部通道内的气流流过气膜冷却孔时，容易在气膜孔入口产生流动分离和漩涡，并由于气膜孔内外压差影响下在气膜孔内形成回流，这些因素对气膜孔形成阻塞效应并对气膜冷却性能造成明显不利影响，这体现在以下几个方面：（1）由于气膜孔内的流动分离和回流形成阻塞效应，会造成气膜孔内冷却空气流量减少，从而直接降低气膜冷却性能；（2）气膜孔口的流动附着和气膜孔内的流动漩涡使得气膜孔内气流流动湍动能增强，这会增强气膜孔出流与外面高温燃气的掺混效应，从而降低气膜冷却效果。特别是，当内部通道内流动与外部主流反向时，当前的气膜孔入口和气膜孔内容易形成大范围的流动漩涡和回流，堵塞了气膜出口流动，大大降低了外部表面气膜冷却性能。
发明内容
有鉴于现有技术的上述缺陷，本发明所要解决的技术问题是能够改善气膜孔与冷却叶片内部流道之间的匹配，从而改善气膜孔入口和气膜孔内的流动状态、提高冷却叶片外部壁面的气膜冷却性能的气膜冷却结构和气膜冷却装置。
为实现上述目的，本发明的第一方面提供了一种用于冷却叶片的凹陷-气膜孔冷却结构，包括设置在所述冷却叶片的内壁的凹陷和贯穿所述冷却叶片的气膜孔，所述气膜孔具有入口，所述入口位于所述凹陷处。
进一步地，所述入口的一部分贯穿所述凹陷所在的壁面，即所述入口的一部分位于所述凹陷所在的壁面上，所述入口的另一部分位于所述冷却叶片的壁面上除凹陷以外的区域。
优选地，所述入口的全部贯穿所述凹陷所在的壁面，即所述入口的全部位于所述凹陷所在的壁面上。
更进一步地，单个所述入口的全部位于一个凹陷所在的壁面上。
更进一步地，多个气膜孔的入口位于一个凹陷所在的壁面上。
进一步地，所述凹陷凹进内壁面中，凹陷的形状为半球形的一部分、带有斜切的球形的一部分、或带有边缘倒圆的曲面或水滴形等，但不限于此。
进一步地，所述气膜孔还具有出口，所述出口位于所述冷却叶片的外壁。
进一步地，所述气膜孔的出口是斜孔、扇形孔、圆柱形孔、棱柱形孔、棱锥形孔或圆锥形孔，但不限于此。
进一步地，所述气膜孔的中心线与所述冷却叶片的壁面的夹角为0~90°，优选为30~60°。
本发明的第二方面提供了一种气膜冷却装置，包括冷却叶片、一个或多个凹陷，以及一个或多个气膜孔，其中所述凹陷设置在所述冷却叶片的内壁，所述气膜孔贯穿所述冷却叶片，所述气膜孔具有入口，全部的所述气膜孔的入口位于所述凹陷处；或者一部分所述气膜孔的入口位于所述凹陷处，另一部分所述气膜孔的入口位于所述冷却叶片的内壁面上除凹陷以外的区域；或者多个气膜孔的入口位于一个凹陷处。
进一步地，当所述气膜孔的入口位于所述凹陷处时，单个所述入口的一部分位于所述凹陷所在的壁面上，单个所述入口的另一部分位于所述冷却叶片的壁面上除凹陷以外的区域。
优选地，当所述气膜孔的入口位于所述凹陷处时，单个所述入口的全部位于所述凹陷所在的壁面上。
进一步地，当多个气膜孔的入口位于一个凹陷处时，所述多个气膜孔的入口位于所述凹陷所在的壁面上。
进一步地，所述凹陷凹进内壁面中，凹陷的形状为半球形的一部分、带有斜切的球形的一部分、或带有边缘倒圆的曲面或水滴形等。
进一步地，所述气膜孔还具有出口，所述出口位于所述冷却叶片的外壁。
进一步地，所述气膜孔的出口是斜孔、扇形孔、圆柱形孔、棱柱形孔、棱锥形孔或圆锥形孔。
进一步地，所述气膜孔的中心线与所述冷却叶片的壁面的夹角为0~90°，优选为30~60°。
在本发明的较佳实施方式中，一种气膜冷却装置，包括冷却叶片和多个上述凹陷-气膜孔冷却结构。
本发明的冷却叶片为涡轮叶片。
相对于现有技术，本发明的优点在于，冷却叶片的内部流道中的流体流过凹陷时，会在凹陷内部形成稳定的低速涡流，并在凹陷内部为气膜孔创造一个良好的入口流动条件，使得气膜孔内的流动更加顺畅，气膜孔内气流的湍动能量也受到抑制。凹陷内部低速稳定的涡流避免了传统方案中内部通道流动在气膜孔入口产生的流动分离、流动附着以及流动回流，因而克服了常规气膜孔设置带来的缺陷，因此本发明的凹陷-气膜孔冷却结构具有更加优秀的冷却性能。特别是，当冷却叶片的内部通道内流动与外部主流反向时，本发明中的气膜孔内的流动漩涡得到显著抑制，气膜孔内流动明显改善，从而显著地提升气膜冷却性能。
以下将结合附图对本发明的构思、具体结构及产生的技术效果作进一步说明，以充分地了解本发明的目的、特征和效果。
附图说明
图1是本发明的一个较佳实施例的气膜冷却装置的结构示意图；
图2是本发明的一个较佳实施例的单个凹陷-气膜孔结构示意图；
图3是本发明的一个较佳实施例的多个凹陷-气膜孔结构示意图；
图4是本发明的一个较佳实施例的凹陷-气膜孔结构的另一示意图，其中多个气膜孔位于一个凹陷处；
图5是当冷却叶片的内部通道内流动与外部主流同向时，本发明的气膜孔内气流流动情况示意图；
图6是当冷却叶片的内部通道内流动与外部主流同向时，现有的气膜孔内流动情况示意图；
图7是当冷却叶片的内部通道内流动与外部主流反向时，本发明的气膜孔内气流流动情况示意图；
图8是当冷却叶片的内部通道内流动与外部主流反向时，现有的气膜孔内流动情况示意图。
具体实施方式
如图1~4所示，本发明的一个较佳实施例提供了一种气膜冷却装置，包括冷却叶片1、一个或多个凹陷2，以及一个或多个气膜孔3，其中凹陷2设置在冷却叶片1的内壁11，气膜孔贯穿冷却叶片1，气膜孔3具有入口，全部的气膜孔3的入口位于凹陷2处；或者一部分气膜孔3的入口位于凹陷2处，另一部分气膜孔3的入口位于冷却叶片1的内壁面11上除凹陷2以外的区域；或者多个气膜孔3位于一个凹陷2处。上述凹陷2和位于该凹陷2处的气膜孔3构成凹陷-气膜孔冷却结构。
本实施例中，当气膜孔3的入口位于凹陷2处时，单个入口的一部分位于凹陷2所在的壁面上，单个入口的另一部分位于冷却叶片1的壁面上除凹陷2以外的区域（图中未显示）。
优选地，当气膜孔3的入口位于凹陷2处时，入口的全部位于凹陷2所在的壁面上。图2和图3显示了单个气膜孔3的入口的全部位于一个凹陷2所在的壁面的情况。图4显示了多个气膜孔3的入口的全部位于一个凹陷2所在的壁面上。
凹陷2的形状可以为半球形的一部分、带有斜切的球形的一部分、或带有边缘倒圆的曲面或水滴形。在其它实施例中也可以根据需要设计凹陷2的形状。
气膜孔3还具有出口，出口位于冷却叶片1的外壁12。气膜孔3的出口可以是斜孔、扇形孔、圆柱形孔、棱柱形孔、棱锥形孔或圆锥形孔。在其它实施例中也可以根据需要设计气膜孔3的出口的形状。
气膜孔3的中心线与冷却叶片1的壁面的夹角为0~90°，优选为30~60°。
本实施例的冷却叶片1为涡轮叶片。
本实施例的气膜冷却装置包括冷却叶片1和单个凹陷-气膜孔冷却结构（见图2）或多个凹陷-气膜孔冷却结构（见图3）；或一个或多个的单个凹陷-多个气膜孔冷却结构（见图4）。图中的箭头4表示冷却叶片外部壁面的气流流动方向，箭头5表示冷却叶片的内部气流流动方向。
相对于现有技术，本实施例的优点在于，冷却叶片1的内部流道中的流体流过凹陷2时，会在凹陷2内部形成稳定的低速涡流，并在凹陷2内部为气膜孔3创造一个良好的入口流动条件，使得气膜孔3内的流动更加顺畅，气膜孔3内气流的湍动能量也受到抑制。凹陷2内部低速稳定的涡流避免了传统方案中内部通道流动在气膜孔3入口产生的流动分离、流动附着以及流动回流，因而克服了常规气膜孔3设置带来的缺陷，因此本实施例的凹陷-气膜孔冷却结构具有更加优秀的冷却性能。
具体地，如图5所示，本实施例中，当冷却叶片1的内部通道内流动与外部主流同向时，气膜孔3内流动顺畅，因而气膜冷却性能更好。而现有技术中，如图6所示，由于气膜孔3入口处没有设置凹陷结构，气膜孔3内存在流动漩涡和回流，阻碍了气膜出口流动，因而降低了气膜冷却性能。图中的箭头4表示冷却叶片外部壁面的气流流动方向，箭头5表示冷却叶片的内部气流流动方向。
如图7所示，本实施例中，当冷却叶片1的内部通道内流动与外部主流反向时，气膜孔3内的流动漩涡得到抑制，气膜孔3内流动顺畅，气膜冷却性能更好。而现有技术中，如图8所示，由于气膜孔3入口处没有设置凹陷结构，气膜孔3内存在大范围流动漩涡和回流，几乎堵塞了气膜出口流动，因而降低了气膜冷却性能。图中的箭头4表示冷却叶片外部壁面的气流流动方向，箭头5表示冷却叶片的内部气流流动方向。
以上详细描述了本发明的较佳具体实施例。应当理解，本领域的普通技术人员无需创造性劳动就可以根据本发明的构思作出诸多修改和变化。因此，凡本技术领域中技术人员依本发明的构思在现有技术的基础上通过逻辑分析、推理或者有限的实验可以得到的技术方案，皆应在由权利要求书所确定的保护范围内。

Claims (10)

  1. 一种用于冷却叶片的凹陷-气膜孔冷却结构，其特征在于，包括设置在所述冷却叶片的内壁面上的凹陷和贯穿所述冷却叶片的气膜孔，所述气膜孔具有入口，所述入口位于所述凹陷处。
  2. 根据权利要求1所述的凹陷-气膜孔冷却结构，其特征在于，所述入口的全部位于所述凹陷所在的壁面上。
  3. 根据权利要求1所述的凹陷-气膜孔冷却结构，其特征在于，所述入口的一部分位于所述凹陷所在的壁面上，所述入口的另一部分位于所述冷却叶片的壁面上除凹陷以外的区域。
  4. 根据权利要求1所述的凹陷-气膜孔冷却结构，其特征在于，所述凹陷凹进内壁面中，凹陷的形状为球面的一部分、或带有斜切的球面的一部分、或带有边缘倒圆的曲面或水滴形等。
  5. 根据权利要求1所述的凹陷-气膜孔冷却结构，其特征在于，所述气膜孔还具有出口，所述出口位于所述冷却叶片的外壁。
  6. 根据权利要求1所述的凹陷-气膜孔冷却结构，其特征在于，所述气膜孔的中心线与所述冷却叶片的壁面的夹角为0~90°。
  7. 一种气膜冷却装置，其特征在于，包括冷却叶片、一个或多个凹陷，以及一个或多个气膜孔，其中所述凹陷设置在所述冷却叶片的内壁，所述气膜孔贯穿所述冷却叶片，所述气膜孔具有入口，全部的所述气膜孔的所述入口位于所述凹陷处；或者一部分所述气膜孔的入口位于所述凹陷处，另一部分所述气膜孔的入口位于所述冷却叶片的内壁面上除凹陷以外的区域；或者多个气膜孔的入口位于一个凹陷处。
  8. 根据权利要求7所述的气膜冷却装置，其特征在于，当所述气膜孔的入口位于所述凹陷处时，单个所述入口的一部分位于所述凹陷所在的壁面上，单个所述入口的另一部分位于所述冷却叶片的壁面上除凹陷以外的区域。
  9. 根据权利要求7所述的气膜冷却装置，其特征在于，当所述气膜孔的入口位于所述凹陷处时，单个所述入口的全部位于所述凹陷所在的壁面上。
  10. 根据权利要求7所述的气膜冷却装置，其特征在于，当多个气膜孔的入口位于一个凹陷处时，所述多个气膜孔的入口位于所述凹陷所在壁面上。
PCT/CN2018/074945 2017-07-13 2018-02-01 用于冷却涡轮叶片的凹陷-气膜孔冷却结构及气膜冷却装置 Ceased WO2019010964A1 (zh)

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